Method for preparing composite solid propellant based on 3D printing special-shaped high-burning-rate pattern mold

Abstract

The invention discloses a method for preparing a composite solid propellant based on a 3D printing special-shaped high-burning-rate model, belongs to the technical field of solid rocket engine manufacturing, and provides a preparation method of a special-shaped high-burning-rate core model / propellant grain integrated structure based on an additive manufacturing technology. The special-shaped high-combustion-rate core mold is formed and prepared through the additive manufacturing technology, the purpose is to form and prepare a high-combustion-rate propellant, and instantaneous large thrust is provided for a solid rocket engine. In the invention, the special-shaped high-burning-rate core mold is prepared by forming propellant slurry, has the characteristics of combustibility and high burning rate, improves the filling ratio of the solid rocket engine, improves the thrust of the solid rocket engine, and is prepared by forming through an additive manufacturing method, and the method realizes the manufacturing of the core mold with a complex structure and improves the design margin of a burning surface structure.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motor manufacturing, and in particular relates to a method for preparing composite solid propellants based on 3D printing special-shaped high-burning-velocity molds. Background technique [0002] High-performance missile weapons require solid rocket motors to have excellent thrust control capabilities, which makes the internal combustion surface of composite solid propellant grains have complex structures. However, in the traditional casting manufacturing process of composite solid propellants, the structure of the internal combustion surface depends on the mandrel. Although coating paraffin on the surface of the mandrel or preparing other coatings will reduce the demoulding process, the internal combustion surface of the complex structure There are the following limitations in the column: 1. In the demoulding process, it is difficult to take out the mandrel with a complex structure; 2. The d...

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Problems solved by technology

However, in the traditional casting manufacturing process of composite solid propellants, the structure of the internal combustion surface depends on the mandrel. Although coating paraffin on the surface of the mandrel or preparing other coatings will reduce the demoulding process, the internal combustion surface of the complex structure There are the following limitations in the column: 1. In the demoulding process, it is difficult to take out the mandrel with a complex structure; 2. The demoulding process will destroy the surface integrity of the internal combustion surface; 3. There are great safety hazards in the subsequent shaping process , these limitations limit the complexity design of the internal combustion surface of the propellant, cannot further improve the energy management capability, cannot realize the refined control of the thrust of the solid rocket motor, and restrict the performance increase margin of the solid rocket motor

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